# D

S.B. 84-54-19 Page 1 of 14 18 Apr 2013 JR 

# SERVICE BULLETIN Customer Support
ATA SYSTEM: 5400 NUMBER: 84-54-19 

### BOMBARDIER AEROSPACE REGIONAL AIRCRAFT CONSIDER THIS SERVICE BULLETIN TO BE PARTICULARLY SIGNIFICANT AND URGES OPERATORS TO PROMPTLY EVALUATE THE CONTENTS

SUBJECT: Nacelle - Special Inspection and Rectification of the A-Frame - ModSum 4-113797

1. PLANNING INFORMATION A. Effectivity Aircraft Affected: In-Service: DHC-8 Aircraft Models 401 and 402 Serial Numbers 4003 thru 4055. Production: The radius increase was incorporated in production using ModSum 4-113159 at Serial Numbers 4056 and subsequent. NOTE: The instructions in this service bulletin are only applicable to the systems and parts installed at the time of delivery on the aircraft or as changed by Bombardier Aerospace Service Bulletin(s). Before you do this bulletin, examine all STC or equivalent action changes to make sure this bulletin can be completed. Spares Affected: None

### SERVICE BULLETIN 84-54-19

S.B. 84-54-19 Page 2 of 14 18 Apr 2013 JR B. Reason Problem: A field inspection on one of the aircraft revealed a condition that was supposed to be corrected during the incorporation of Service Bulletin 84-54-04 (ModSums 4-113279 and 4-113305) was not accomplished. This condition was an insufficient fillet radius on the A frame base flange. Solution: This service bulletin provides instructions to do an inspection to check for the insufficient fillet radius condition & cracks and to repair the condition if existing. C. Description The procedures in this service bulletin give the instructions to do the tasks that follow: - aircraft electrical power is removed - the nose landing gear lock is engaged - the main landing gear lock pins are installed thru each main gear and main gear door mechanism - an inspection is done to check the A frame base flange for a insufficient fillet radius and cracks - if an insufficient fillet radius is found and no cracks are found, aircraft is rectified using instructions provided in this service bulletin - if cracks are found, operators are to contact the Help Desk/Action Center for further instructions - If sufficient fillet radius is found, aircraft can be returned to service. - close out. D. Compliance Bombardier Inc. recommends incorporation of ModSum 4-113797 at the earliest opportunity unless otherwise directed by the operator’s airworthiness authority. A Transport Canada Airworthiness Directive is pending

### SERVICE BULLETIN 84-54-19

S.B. 84-54-19 Page 3 of 14 18 Apr 2013 JR E. Approval The technical content of this service bulletin has been approved under the authority of the Transport Canada Civil Aviation (TCCA) Design Approval Organization No: DAO #93-Q-02. This service bulletin does not affect Airworthiness Limitations (AWLs) or Damage Tolerance Inspections (DTIs). F. Manpower PART A - Inspection It will take an estimated 1.50 man-hours to complete PART A of the ACCOMPLISHMENT instructions in this service bulletin. The breakdown of man -hours is shown in the table that follows: TASK MAN-HOURS Job Set-Up 0.25 Procedure in Part A 1.00 Test / RTS 0.00 Close-Out 0.25 PART B - Rectification It will take an estimated 2.50 man-hours to complete PART B of the ACCOMPLISHMENT instructions in this service bulletin. The breakdown of man -hours is shown in the table that follows: TASK MAN-HOURS Job Set-Up 0.25 Procedure in Part B 2.00 Test / RTS 0.00 Close-Out 0.25 For any on-site labor assistance, please speak with a Fleet Services representative for a quote. The Fleet Services group can be contacted via the Q Series Technical Help Desk by telephone at 416-375-4000 or email at: thd.qseries@aero.bombardier.com

### SERVICE BULLETIN 84-54-19

S.B. 84-54-19 Page 4 of 14 18 Apr 2013 JR G. Material - Price and Availability None H. Tooling - Price and Availability None I. Weight and Balance None J. Electrical Load Data Not affected K. Publications Affected ModSums Manual PSM 1-84-12

.................................. L. References The initial issue of this service bulletin was prepared to the engineering drawings and related data that follows: DRAWING SHEET REV

8DK4211 1
--

8Z9806 1
-- ModSum 4Q113797 Rev. ‘B’ ModSum 4-113797 Rev. ‘B’ PCA 44090 Revision 0 (for internal reference only) A Transport Canada Airworthiness Directive is pending 2. MATERIALINFORMATION A. Parts Required Per Aircraft None (1) The following materials are required for the completion of this service bulletin and may be procured as single items from Bombardier Aerospace Regional Aircraft or purchased directly from industry sources.

### SERVICE BULLETIN 84-54-19

S.B. 84-54-19 Page 5 of 14 18 Apr 2013 JR For alternative equivalent materials, refer to Consumable Products Manual (CPM) PSM 1-84-18.
Part Number Qty. Per Aircraft Description Alternative Equivalent DHMS C4.01 Type 2 (F19) as required Primer Chromated Epoxy see CPM section 07-02 MIL-C-5541 (C1) as required Chemical Conversion Coating see CPM section 07-29A DHMS C4.04 (F24) Type 4, Class A as required Polyurethane Enamel see CPM section 07-08 B. Parts Required to Modify Spares None C. Special Tools and Equipment Required None D. Existing Parts Accountability None 3. ACCOMPLISHMENTINSTRUCTIONS A. Job Set-Up

WARNING: MAKE SURE YOU INSTALL THE LOCKPINS ON THE MAIN LANDING GEAR. MAKE SURE YOU ENGAGE THE NOSE GEAR LOCK. IF YOU DO NOT DO THIS, THE LANDING GEAR CAN ACCIDENTALLY RETRACT. THIS CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO THE EQUIPMENT. WARNING: MAKE SURE YOU INSTALL THE LOCKPINS IN THE DOOR MECHANISMS OF THE MLG AND NLG. THE DOOR MECHANISMS CAN ACCIDENTALLY CLOSE THE LANDING GEAR DOORS. THIS CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO THE EQUIPMENT. (1) Placard and select all aircraft electrical power to OFF. Obey all relevant WARNINGS and CAUTIONS (refer to AMM TASK’S 24-00-00-861-802 and 24-00-00-910-801). (2) Make sure that lock pins are installed through each main gear and main gear door mechanism.

### SERVICE BULLETIN 84-54-19

S.B. 84-54-19 Page 6 of 14 18 Apr 2013 JR (3) Make sure the nose gear ground lock is engaged. (4) Set up the work platforms or ladders as required to gain access to the A frame in each nacelle. Make sure the work platforms or ladders are electrically grounded. B. Procedure Part A -Inspection (1) On the left and right nacelle inspect the A-Frame aft face, base flange transition adjacent to the drag strut fitting attachment to determine if a 0.500 + or - 0.03 inch radius is produced in the base flange of the A-Frame 8Z8527, refer to Figure 6. NOTE: Rework strap 8Z8534-103 is already manufactured with 0.500 + or - 0.03 inch radius (2) If 0.500 + or - 0.03 inch radius already exists in base flange of A-Frame 8Z8527 at 2 locations per nacelle, no further work is required. Proceed to Close Out section of this service bulletin. (3) If 0.500 + or - 0.03 inch radius does not exist in base flange of A-Frame 8Z8527, inspect area using eddy current crack detection or fluorescent dye penetrant per Nondestructive Testing Manual, PSM 1-84-7A. (4) If there are any cracks, contact Bombardier Help Desk/Action Center for approved repair instructions. (5) If there are no cracks, proceed to Part B - Rectification section of this service bulletin. Part B -Rectification CAUTION: PROTECT HYDRAULIC LINES AND HARNESS’S NEAR REWORKED AREA FROM DAMAGE DURING MATERIAL REMOVAL. (FIGURE 3) (1) Remove material from A-Frame 8Z8527 as shown in Figure 6, Detail E. NOTE: Care should be taken to maintain edge distance of 0.32 inch minimum to hi-lite hole for drag strut, also make sure no damage to shear deck 8Z8536 and rework strap 8Z8534-103. (2) Finish machined edges per Structural Repair Manual PSM 1-84-3, Chapter 51-14-00. (3) Clean cut metal edges per Structural Repair Manual PSM 1-84-3, Chapter 51-26-00.

### SERVICE BULLETIN 84-54-19

S.B. 84-54-19 Page 7 of 14 18 Apr 2013 JR (4) Improve cut metal edges to achieve a surface finish of 125RMS or finer. (5) Re-finish reworked areas using the following materials: (a) Chemical Conversion Coating (C1) per Structural Repair Manual PSM 1-84-3 Task 51-21-10-02-02. (b) Epoxy Primer (F19) per Structural Repair Manual PSM 1-84-3 Task 51-25-10-02-01. (c) Polyurethane Enamel (F24) per Structural Repair Manual PSM 1-84-3 Task 51-25-15-02-01. (6) Re-identify LH Frame as 8Z9806-001 and RH Frame as 8Z9806-002 per Aircraft Maintenance Manual PSM 1-84-2 Task 20-00-01-910-801. (7) After identification markings have dried, apply clear coat (no colour) of Polyurethane Enamel (F24) per Structural Repair Manual PSM 1-84-3 Task 51-25-15-02-01. C. Close Out (1) Remove all tools and equipment from the work area. (2) On incorporation of this ModSum, make an entry that conforms to local regulatory requirements in the applicable logbook(s). Enter component serial numbers if applicable. Enter this ModSum number only after complete and functional incorporation of all work defined in this service bulletin.

### SERVICE BULLETIN 84-54-19

S.B. 84-54-19 Page 8 of 14 18 Apr 2013 JR Area of Work Figure 1

### SERVICE BULLETIN 84-54-19

S.B. 84-54-19 Page 9 of 14 18 Apr 2013 JR A-Frame Figure 2 A-FRAME 8Z8527

REWORK STRAP 8Z8534-103

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S.B. 84-54-19 Page 10 of 14 18 Apr 2013 JR Figure 3 A-FRAME 8Z8527

REWORK STRAP 8Z8534-103

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S.B. 84-54-19 Page 11 of 14 18 Apr 2013 JR Figure 4 REINFORCEMENT STRAP 8Z8534

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S.B. 84-54-19 Page 12 of 14 18 Apr 2013 JR Figure 5

### SERVICE BULLETIN 84-54-19

S.B. 84-54-19 Page 13 of 14 18 Apr 2013 JR Figure 6 EXISTING INSUFFICIENT FILLET RADIUS

DETAIL ‘E’ SYMMETRICAL ABOUT CENTER LINE OF EACH NACELLEMAINTAIN 0.500 + or - 0.03 INCH RADIUS ON REWORK STRAP 8Z8534-103 A-FRAME 8Z8527 MATERIAL TO BE REMOVED

REWORK STRAP 8Z8534-103 (no rework necessary if 0.500 + or - 0.03 inch radius exists)

A-FRAME 8Z8527

### SERVICE BULLETIN 84-54-19

S.B. 84-54-19 Page 14 of 14 18 Apr 2013 JR 

### This Page Intentionally Blank. 1Jan 2009 SERVICE BULLETIN (SB) --- RECORD OF INCORPORATION --- Q SERIES DASH 8 AIRCRAFT To: CMDB Focal Facsimile: (1) 416 375 4538 E --mail: cmdb.requests@aero.bombardier.com From: Company: Phone: Extn: Facsimile: Date:

E --mail: The data that you provide below will help us record the incorporation of this ModSum and the aircraft effectivity in the maintenance manual. Operator: Service Bulletin:

__________________Revision:

_________ Aircraft Serial Number: Model Number: Date Bulletin Completed: Aircraft Serial Number: Model Number: Date Bulletin Completed: Aircraft Serial Number: Model Number: Date Bulletin Completed: Aircraft Serial Number: Model Number: Date Bulletin Completed: Aircraft Serial Number: Model Number: Date Bulletin Completed: Aircraft Serial Number: Model Number: Date Bulletin Completed: Aircraft Serial Number: Model Number: Date Bulletin Completed: Aircraft Serial Number: Model Number: Date Bulletin Completed: Aircraft Serial Number: Model Number: Date Bulletin Completed: Aircraft Serial Number: Model Number: Date Bulletin Completed: Aircraft Serial Number: Model Number: Date Bulletin Completed: Aircraft Serial Number: Model Number: Date Bulletin Completed: 

## Fax this sheet to (1) 416 375 4538 or Email PDF to: 

# cmdb.requests@aero.bombardier.comFeb 2009 SERVICE BULLETIN (SB) --- COMMENT SHEET --- Q SERIES DASH 8 AIRCRAFT

To: SB Focal (Toronto), Bombardier Aerospace Commercial Aircraft Phone: (1) 416 375 4078 Facsimile: (1) 416 375 4538 E --mail: syed.rizvi@aero.bombardier.com From: Company: Phone: Extn: Facsimile: Date:

E --mail: Select appropriate box(es) and add comments or suggestions you would like us to know that may enhance the quality of our service bulletins. Service Bulletin: Revision: ModSum: 1. PLANNING INFORMATION V Effectivity V Reason V Description V Compliance VApproval V Manpower V Material VWeight and Balance V Electrical Load VTooling V References V Publications Affected 2. MATERIAL INFORMATION V Kit Content V Special Tools/Equipment V Parts to Modify Spares V Consumables V Disposition of Existing Parts V Other
3. ACCOMPLISHMENT INSTRUCTIONS V Job Set ---Up V Procedure V Close---Out VTest V Illustration(s) V Other 4. COMMENTS, REMARKS, SUGGESTIONS



## Fax this sheet to (1) 416 375 4538 or Email PDF to: syed.rizvi@aero.bombardier.com